Gimbaled Mount System for Satellites

ABSTRACT

Described herein is a method and system for gimbaled mounting of satellite dishes. The gimbaled mount for satellite systems overcomes some of the most common negative events affecting satellite communications. The system is a cost effective solution that amortizes the cost of the additional equipment to well over the customary three to five years for satellite use and extends its working life expectancy to 20 years or more. Utilization of stainless steel rather than normal steel or lighter duty aluminum further extends the mounting systems longevity. The inclusion of an environmental feedback system for both snow and ice damage, wind damage, and earthquake damage increases the projected useful life of the mounting system.

CROSS-REFERENCES TO RELATED APPLICATIONS

This application claims the benefit of U.S. Provisional Application No.60/886,905 filed Jan. 26, 2007, the contents of which are incorporatedherein by reference.

FIELD OF THE INVENTION

The present invention was designed as primary component within a largercommunications system. This proposed communications component addressesthe need for a more robust connection between devices that may be reliedon during an emergency or security event and cannot be allowed to failwhile facilitating security and normal communications services duringnormal times. The nature of this design allows for variation in capacityand size within tight design constraints that insure compliance with theengineering principles that insure performance during a stressfulsituation whether the actions are thermal or mechanical in nature.

More particularly, the present invention addresses the need for areliable weather resistant mounting system for satellites.

BACKGROUND OF THE INVENTION

Satellite communications in the past required precision alignment of thedish system, to comply with an aperture of 1.5 to 2.0 degrees maximummovement to be still adequately in the download or upload beam to permitproper data or signal transfer. This critical alignment can easily bethrown out of alignment during an earthquake, building or groundsettling condition, or severe weather wind type calamity.

Satellite communications systems, once they are aligned, are consideredto be more robust than terrestrial communications lines, especially whenthose lines are subject to events such as an earthquake, flood, or highwind condition.

Typically satellite systems are put into operation some time duringtheir life span, typically 15 years for a specific satellite. Anycorrective positioning, which has occurred on several satellites inorbit currently and in the past, requires direct technical support andre-alignment of the earth station equipment to take into account thepositional movement.

Weather conditions are notorious for knocking out satellite earthstations and the smaller lower cost ones are very susceptible to weatheroutages. Larger network type earth stations usually or robust enoughboth in diameter and construction materials to withstand numerousweather events during their planned life span without causingunpreventable weather outages. Excluding rain fade which can only beaddressed by larger dishes makes the smaller the dish more susceptibleto snow and ice.

Typical wind loading on a dish, and more so on the larger the dish, canthrow alignment, temporarily or permanently until a technician canre-align the earth station dish assembly. In view of extensiveexperience with conventional earth stations, it is believed thatconventional earth stations lack any self compensating mechanism, exceptfor those conventional stations that are fully motorized. Furthermorethe awareness or call out for re-alignment of earth stations has beenmore than the norm in the past, especially on small aperture dishes suchas a Very Small Aperture Terminal (VSAT), which is a two-way satelliteground station with a dish antenna that is smaller than 3 meters.Especially after a storm or serious snow fall, VSAT re-alignment may beneeded.

Construction of most earth stations is made out of standard steelcomponents with at the most only the primary bolts being made ofstainless steel. This leads to much needed maintenance and paintingneeding to be the VSAT to be down to maintain the appearance, to reducecorrosion, and to maintain functionality of the typical earth station.

Snow and ice can be detrimental to proper earth station operation. Attimes, on larger systems, crews may even have to go out and sweep offthe snow to stop its affect on the large dishes. Similarly the buildupof ice from snow melting on the warm electronics located at the feedassembly can cause serious ice loading lower on the dish. Smaller homeor commercial VSAT type dishes are notorious for loosing satelliteconnectivity during heavy snow fall till someone goes out and cleansthem off.

SUMMARY OF THE INVENTION

It is an object of the present invention to obviate or mitigate at leastone or more disadvantages of previous communications systems.

A Gimbaled Mount Satellite System in accordance with the presentinvention may only need to be critically aligned once during initialinstallation and all subsequent weather or environmental factors actingupon the system may be dealt with by the earth station facilities builtinto the Gimbaled Mount Satellite System, in accordance with the presentinvention.

The unique design incorporated a Gimbaled Mount Satellite system, inaccordance with the present invention, uses the principles of gimbalswhich like a sea compass, uses the earths gravity pulling downperpendicularly on the suspend device to keep it flat surfaced andviewable to the viewer.

The unique mechanical design of the Gimbaled Mount System uses nearfrictionless pivotal bearings rather than typical sealed ball or rollerbearings for all pivot points. This may allow for many years ofunattended operation for a typical system.

The construction of the Gimbaled Mount System may be made almostentirely out of high grade, heavy gauge stainless steel construction,which may eliminate the need for painting and preventing rust fromaffecting its long term continuous operation and extending its lifespan.

The low profile, low wind resistance design and adjustable mounting legsalong with compact non-penetrating foot print makes the Gimbaled MountSystem ideal for most flat or near flat roofs.

The incorporation of a low-power-demand-wind dampening system within thedesign of the Gimbaled Mount System may improve not only system survivalfollowing a high wind event but also the continuous operation of theearth stations primary function during a severe wind event.

Weather conditions vary significantly around the world, and snow or icecan be part of that common event. A Gimbaled Mount System, in accordancewith the present invention, has an option for fully designed de-icing orsnow melting system, which may prevent any such local weather problemfrom interfering with the operation of the earth station.

A Gimbaled Mount System in accordance with the present invention, maynot need for an exterior bubble or dome type enclosure, thereforeproviding the ability to support multiple sizes of satellite dishes inboth circular and elliptical designs, with only the center balance pointneeding to be determined before securing to the lower mounting plate.

Several suitable applications result from methods and devices describedherein. Those skilled in the art will further appreciate the above-notedfeatures and advantages of the invention together with other importantaspects thereof upon reading the detailed description that follows inconjunction with the drawings.

BRIEF DESCRIPTION OF THE DRAWINGS

For more complete understanding of the features and advantages of thepresent invention, reference is now made to a description of theinvention along with accompanying figures, wherein:

FIG. 1 is drawing of a Gimbaled Mount Satellite System, showing itsmechanical low profile design from a side view, in accordance with anexemplary embodiment of the present invention;

FIG. 2 is a detailed Gimbaled Mount Technical Drawing used forfabrication, with several notations as to the components making up thisoverall exemplary assembly;

FIG. 3 is Blown up drawing detailing the pivot bearing design function,with note 11 detailing a pivot point and V-groove relationship detail;

FIG. 4 is an End view of Drop Center Pivot Point Mounting;

FIG. 5 is a drawing of legs and feet for a Gimbaled Mount in accordancewith the present invention, with several notations as to componentsmaking up this assembly;

FIG. 6 is a drawing of the Gimbaled Mount wind dampening system, withseveral notations of components within this assembly;

FIG. 7 is a Detailed drawing of the Platform (note 12) including anchorpoint pin (note 16) for stabilizer springs and Pivot hanging points(note 13);

FIG. 8 is a Manual Wind Dampening System detail drawing, includingseveral notations for components within this assembly;

FIG. 9 is The Electric Automatic Wind Dampening System, with severalnotations regarding both the electric stepper motor winch and Aerometerfeedback unit; and

FIG. 10 is a Drawing showing the path or placement of The ThermalProtection System of the Gimbaled Mount, as it relates to the dish andLNB assembly and overall Gimbaled Mount including pivot points is shown.

DETAILED DESCRIPTION

The Figures collectively represents actual sub sections of thefabrication drawings for the CommPuter controller communicationscontroller, as disclosed in U.S. Provisional Patent Application No.60/886,905, and which is incorporated herein by reference.

A Gimbaled Mount System design, in accordance with the present inventionwas derived from experience with the repeated historical failure ofearth stations, that were required for communications purposes, beingmade inoperable following either an earthquake, that shifted theposition of an existing structure, or where wind damage had occurred.The present invention addresses a design which is a component part of amuch larger approach to emergency communications previously disclosed inU.S. Provisional Patent Application No. 60/886,905. The design andmethod described herein provides a method to recreate or fabricate, afully functional device that significantly addresses the short falls orfailures of previous systems and provides a more robust method ofcreating a earth station satellite system. The entire mechanism orinvention may be manufactured out of stainless steel further, which mayassure that this design may have a substantially longer lifespan then atypical earth station mechanism, which is made out aluminum and regularsteel. The present invention compensates, at least in part, for windstorm or ice or snow build up has been taken into consideration and mayensure no outages for the this type of earth station. The construction,in accordance with the present invention may also benefit the buildingowner or manager to which this earth station is installed as it does notrequire large ballast materials to weigh down the structure nor does itrequire roof penetration for any of the mounting system.

A Gimbaled Mount System, in accordance with an exemplary embodiment ofthe present invention, begins with all components being manufactured outof heavy gauge marine grade stainless steel, typically of 0.025 inchthick material. This insures that corrosive weather action or chemicalswill not affect the longevity of this system. The intention of thisconstruction from the selection of every component is designed withconsideration of this earth station remaining operable for 20 years. Assatellite's in orbit generally do not last this long, the ability toeasily align to an alternate satellite has been built into the basicdesign of this system. FIG. 1 shows a side view of a Gimbaled MountSatellite System 100, in accordance with an exemplary embodiment of thepresent invention. Its low profile design 105 is shown from this sideview, where the legs 107 are 24 inches high and the satellite dish 115,shown in this particular embodiment, is 24×36 inches.

FIG. 5 is a drawing of legs and feet for a Gimbaled Mount in accordancewith the present invention, with several notations as to componentsmaking up this assembly The legs, in accordance with an exemplaryembodiment of the present invention, as detailed in FIG. 5, are madefrom a 24 inches long post 2, having a 1.00 inch O.D. stainless steeland a 0.125 wall thickness pipe. A slot 12, at least 2.00 inches deepand 9/32 inch wide, is cut at the middle of the top end of this pipe forsliding into a socket made on the outer 0.250 inch by 2 inches gimbaledring. Also shown in FIG. 5 are: 53 adjustable leg screw; 4 foot plate; 5adjustable leg locknut; 7 leg post top plate; 19 leg ring for tensioncable pulley; and 6 a, b, c, d respective leg alignment plates, whereonly one of four is shown.

A 2 inch high by 0.250 inch thick stainless steel ring is rolled andcurved into 2 sections with overlapping and bolted ends, forming the48.0 inch outer ring. The bolt to hole ratio is tight so as to notcreate any flex in this ring when fully assembled. At the mid-point ofeach half section, or directly opposite each other on the overall 48.0inch ring are cut 2 “V” grooves at approximately 45 degrees arc (seeFIG. 3 note 11). FIG. 3 is a blown up drawing detailing the pivotbearing design function, with note 11 detailing a pivot point andV-groove relationship detail.

Similarly, in accordance with the present invention, on the 2 inch by0.250 inch thick stainless steel outer ring, spaced exactly 90 degreesapart, equidistant from each other, are located 4×0.750 inch by 4 inchlong, with a 9/32 inch slot×2 inches long, stainless steel pipe sectionswelded to outer ring, with the 2 inch extension hanging below the outerring. This permits the Legs as described above to socket rigidly intothe outer ring for stable operation.

The legs, in accordance with an exemplary embodiment, all have a 0.125inch thick by 1 inch diameter round plate 527, with a captured andwelded 0.625 threaded diameter nut and mating 5 (see FIG. 5 note 55).700 hole on the plate. This permits a mating ⅝ inch threaded stock by 12inches long rod 53 to be screwed in along with a 2 inch diameter by0.125 thick end plate 5 welded to one end of the adjustable rod to actas the load bearing plate in contact with the roof. A ⅝ inch matinglocking nut is pre-loaded to each rod during manufacturing to insure therod does not go all the way into the leg socket and to also lock theposition of each leg once the outer ring is made perfectly level.

The outer ring 1, as shown in FIG. 2, top view, in accordance with anexemplary embodiment, is constructed in two sections to ease in takingcomponents up a standard elevator to the rooftop installation. Once theouter ring is made perfectly level, using either a 5 foot long bubblelevel or 24 inch with a straight board, and spanning the entire outerring diameter, the leg's lock nuts are tightened. This ensures nomovement of the outer ring and a stable platform to build the gimbaleddeck from.

The inner ring 8, in accordance with an exemplary embodiment, isconstructed similar to the outer ring 1 of 2 inch high by 0.250 thickstainless steel, however the diameter when assembled is 4 inches smallerthan the outer ring. Mid-Point on each arc of the Inner Ring is a weldeddrop type L-bracket 9. The protruding 3 inch portion of the thisL-bracket has a beveled knife edge that will align with the twoV-grooves in the Outer Ring. The L-bracket 9 lowers the Inner ring whensuspended on the Outer Ring by 2 inches beginning the gravitationaloffset point. The mid-point opposite each other is additional V-groovesfor accepting the Platform Plate.

The Platform Plate 12, in accordance with an exemplary embodiment, (seeFIG. 7 note 12) is constructed and welded in one piece primarily withsimilar L-brackets 13 that rest in the V-grooves cut in the Inner Ring.Once again, the L-brackets 13 drop the Platform Plate approximately 4inches from the height of the Inner Ring. The final assembly procedurefor the Platform Plate is screw in on the underside of the PlatformPlate in captured nut, the Dampening Spring Anchor Pin (see FIG. 7 note16). Summarizing FIG. 2 shows: 1 Outer Gimbals Ring; 2 a, b, c, d, 24inch leg posts; 3 adjustable leg screw; 4 foot plate; 5 adjustable leglocknut; 6 a,b,c,d leg alignment plates; 7 leg post top plate; 8secondary inner ring; 9 a, b welded pivot L-brackets; 11 V groove pivotpoint; 12 platform plate; 13. platform plate L-brackets; 14 tensionsprings; 15 Dampening cables; 16 Anchor Pin; 17 Leg post pulley; 18Aerometer mounting point; and 19 close-up leg ring for tension cablepulley.

Once the 2 rings and Platform Plate have been assembled and placed onthe legs, the gimbaled operation begins. The next step is to take thedish and its plate mount system and bolt it to the correct holes on thePlatform Plate to achieve balance when the Dish is mounted. The boltslots in the Platform Plate allow for front to back movement of the DishMount plate and are positioned to accommodate several different dishsize configurations. Once the Dish is properly mounted applying slightpressure to the Dish should cause the entire Platform Plate to move.Taking pressure off in a none windy condition should cause the Dish toreturn to “Plumb” state. Gravity does all the work to this point. TheDish although able to be roughly pointed at the correct satellite atthis point, should be avoided till the Dampening System is installed.

Each of the 24 inch legs, and approximately 8 inches down from the top,if each tube, is welded a 1 inch×¾ inch hook, used for connecting orhanging a pulley with eyelet assembly for the wind dampening system. Onone leg only, and before the foot post was fully inserted atmanufacturing a spooling system is slid over the tube. (See FIG. 8) Inconstant wind loading areas a manual drum and tension system isutilized.

However, in wind conditions, a mounting system embodiment includes aremotely operated electric drum winch mechanism which is mounted on oneof the legs pointing towards the inside of the Gimbaled Mount assembly.This is remotely operated, by an attached CommPuter controller system asdisclosed both in U.S. Provisional Patent Application No. 60/886,905,and as also disclosed in US. Application No., filed concurrentlyherewith, both which are incorporated herein by reference. A wind speedaerometer is inserted into the top side of the Outer ring assembly intothe leg assembly holding the Winch assembly. A common service cableinterconnects both the lower Winch unit and the aerometer for wind speeddetection and CommPuter controller feedback which causes either theWinch to take up slack or release slack to the dampening cables.

The Dampening cables 15, in accordance with an exemplary embodiment, usean eyelet formed in the end located near the center of the GimbaledMount, and are attached to 4 long coil springs 14 with eyelets at eachend, as shown in FIG. 6. (See FIG. 6 item 14) One end of the Dampeningsprings 14 is attached to the dampening cables 15 while their oppositeends are hooked over the Center Pin 16 of FIG. 7. Pin 16 extends downfrom the Center Platform 12 of the Gimbaled Mount, as shown in FIG. 7.

The Dampening cables, when in an area with low wind problems, may beused with a Manual Wind Dampening System, as shown in FIG. 8. GimbaledMount System leg is modified to have a stop ring 22 welded approximately13 inches down from the top of the post 2 (see notation #22 in FIG. 8and in FIG. 9).

Once the Dampening cables 15 are secured to the loose end of theDampening Springs 14, the opposite end of the cable is routed back totheir respective Legs #1, #2, #3 through respective pulleys 17 hookedinto the hook welded on 3 of 4 Legs and then the cables are directed tothe fourth Leg, spooling system. The shorter cable, of the 4 cables issecured to Dampening Spring 14, and directed at Leg #4, and enters thespooling system, directly. FIG. 9

All Loose ends are looped once around the Spool drum core. The Looseends are threaded through holes in the core of the Dampening Spoolassembly. Cables are then brought taunt and secured without anystretching of the Dampening Springs. The stretching of the DampeningSprings is left to the Spool drum assembly.

The Manual Wind Dampening System, in accordance with an exemplaryembodiment, and its spooling system, as shown in FIG. 8 has a ¼ inchlocking bolt in the extend hub that locks the Spool when correct tensionhas been reached. The rotating of the Dampening Spool causes all tensionsprings to be equally tension loaded. This acts as a shock or windsensitivity reducer and allows minor breezes to buffet the dish assemblywithout causing the Gimbaled Platform and subsequently the Dish fromvarying off the critical alignment directed at its specific satellite.FIG. 8, a Manual Wind Dampening spool, in accordance with the presentinvention, shows: 2 a 24 inch post tube; 3 adjustable leg screw; 4 footplate; 5 adjustable leg locknut; 6 adjustable leg guide nut; 7adjustable leg stabilizing plate; 20 Manual Dampening spool adjustmentcollar; 21 Manual Damping spool collar lock bolt; and 22 Dampening spoolcollar welded stops.

The Electric Automatic Wind Dampening System, in accordance with anexemplary embodiment, as depicted in FIG. 9 is comprised of two maindevices affixed to Leg #4. The first device is an Electric Stepper Motordriven spooling system as shown by notation #19 in FIG. 9. This StepperMotor is mounted on a slide on sleeve and bracket assembly as shown inFIG. 9. The Stepper Motor is connected by a common control cableassembly that is shared by the Aerometer unit and routed back to theCommPuter controller as previously disclosed in U.S. Provisional PatentApplication No. 60/886,905, and also disclosed in detail under aseparate concurrent filing U.S. Application No. TBD. FIG. 9 shows theElectric Auto Dampening Spool, in accordance with an embodiment of thepresent invention. FIG. 9 shows: 2 Dampening Spool mounting collar; 3Adjustable leg screw; 4 foot plate; 5 adjustable leg locknut; 6adjustable leg guide nut; 7 adjustable leg stabilizing plate; 19Dampening spool with anchor slots; 22 Dampening spool collar weldedstops; 24 Aerometer assembly with cups and servo; and 25 Dampening spoolStepper Motor.

The Second part of the Electric Automatic Wind Dampening System is anAerometer as depicted as note #24 in FIG. 9. The Aerometer iselectrically connected by a common control cable along with the StepperMotor assembly back to the CommPuter controller System as previouslydisclosed in U.S. Provisional Patent Application No. 60/886,905, andalso disclosed in detail under a separate filing under a separateconcurrent filing U.S. Application No. TBD.

The Action of wind turning the Aerometer cups (see FIG. 9 note 24)causes a signal voltage relative to current wind speed to be fed back tothe CommPuter controller Command Processor circuit on the SegmentedAddressable Communications Assembly (SACA) Junction Box motherboard asdefined previously in and as previously disclosed in U.S. ProvisionalPatent Application No. 60/886,905, and also disclosed in detail under aseparate concurrent filing U.S. Application No. TBD. This input voltageis read by the Command Processor and either a rising or falling windspeed instructs the Command Processor to issue a forward for increasingor reversing for falling wind speed command to the Stepper Motor circuitand fed back up the common control cable, where the Electric Spoolingsystem (see FIG. 9 note 25) either takes cable in tightening thedampening springs or loosening to relieve tension off the dampeningsprings uniformly.

The action of stretching or applying more tension to the springs (seeFIG. 6 note 14) equally in 4 diametrically different directions causes adampening or semi-restrictive action on the natural externally inducedwind drag motion on the dish which due to size and angle is amplified inits reactive actions to the Platform to which it is applied. In aconventional roof top or larger earth station design, natural mass orthe addition of weighted blocks or bags placed on the earth station baseplate mounting system. Typically this can also cause great hardship onthe installer when having to carry these heavy ballast weights to theroof to hopefully secure the dish and mount assembly or earth station.The ballasts act as a restrictive force on efforts of the wind to topplethe rigid dish and mount assembly or earth station. Ballasts are thenorm for the telecommunications industry as piercing the roof membraneto secure a dish and mount assembly or earth station, is highly frownedupon due to liability for roof leaks.

The primary advantage and choice point between the Manual (see FIG. 8and the Electric Automatic Dampening Systems (see FIG. 9) is the abilityof the later to react to the unexpected. The principles and uniquenessof the Gimbaled Mount System over conventional choices for the sameapplication, is that a Gimbaled Mount System is designed to survive andnot fail when communications are most needed. Like a Public TelephoneSystem that is built to Telcordia© Standards of 5×9's or 99.999 percentuptime, the Gimbaled Mount System brings this type of unique reliabilityto wireless satellite communications unlike any other system before it.

Wind is not the only threat to satellite systems, snow and ice damagecan directly affect the operations of satellite dish or earth station.Snow laden dishes effectively change their parabolic curve thereforebecoming less or non effective for receiving the weak satellite signals.Customary sweeping or brushing off the dish surface takes labor andsometimes results in temporary outages until the snow or ice is removed.By Installing a thermal heating cord, in accordance with an exemplaryembodiment, along the backside of the Dish as detailed in attacheddrawings (see FIG. 10), the underside of the Low Noise Amplifier module,and crucial pivot points on the Gimbaled Mount assembly, the dish withonly the aide of a thermostat set, for example, at 34 degrees Fahrenheit(1 degree Celsius) keeps the Dish clear of snow or ice, and the pivotsremain unclogged while the dish operation is maintained even through amajor snowfall or ice storm.

The construction of the gimbaled portion of the mount assembly will nowbe disclosed in detail, in accordance with an exemplary embodiment.Inset 2 inches in from the Outer Ring is the Inner Ring a secondarysupport ring with two exactly opposite 2 inch drop offset pivot bracketsmade of stainless steel welded to the secondary ring. The supportportion of the L-bracket allows the ring to sit 2 inches lower than thetop surface of the outer main ring. The L-brackets as detailed in FIG.3, allows the 43.5 inch diameter Secondary Ring, to pivot on these twobrackets when a blade or wedge type extension with case hardened pivotsurface point rests in matching V-grooves prepared in the Primary 48inch diameter outer Primary Ring. The Secondary Inner Ring also has,directly opposite each other, 2 V-grooves cut in the top edge of thisRing. Ordinarily this would continue to make the Inner Ring unstable,however from these 2 V-grooves in the Secondary Ring to 4 inch hightriangle type plates as detailed in FIG. 4 with similar mating bladeextensions welded onto, rest in these 2 v-grooves.

The Platform, in accordance with an exemplary embodiment is shown inFIG. 7 in this overall assembly is a disc like 39 inch diameter platformfor the satellite dish equatorial mount to be attached to. Variousmounting holes in the Platform allow for minute adjustment of theposition of several different types of Dishes and Equatorial Mounts tofastened and still maintain a balance point relative to the side mountedPivot plates. The installer uses once again a 4 foot bubble level, toestablish actual flat position of the Platform. The actual weight of theDish and Mount assembly along with the weight of the Platform assemblyitself when dropped drop 3 inches below the pivot points (see FIG. 7note 13) causes the Platform to remain stable and plum to agravitational point, much like a ships compass does in a rolling sea.

At the dead center of the 39 inch diameter Platform Plate and extending3 inches down is the Stabilizer Spring Anchor Pin, (see FIG. 7 note 16).This Pin along with the Wind Dampening System and spring assemblieskeeps the stability of the Platform constant even with wind drag on thetopside dish assembly. The Aerometer (see note #23 in FIG. 9) detectsthe wind speed, feeds back a proportional voltage to the CommPutercontroller where the on-board Command Processor located on the HerculesSACA Junction Box motherboard translates the voltage to an appropriateoutput command back up the same common cable to the Stepper Motor (seeFIG. 9 note 25) winch system which increases or decrease the rotation ofthe winch drum thereby pulling more or less on the Dampening Springs(see FIG. 6, note 14) and thereby dampening or negating the effect ofthe wind drag on the dish assembly.

While specific alternatives to steps of the invention have beendescribed herein, additional alternatives not specifically disclosed butknown in the art are intended to fall within the scope of the invention.Thus, it is understood that other applications of the present inventionwill be apparent to those skilled in the art upon reading the describedembodiments and after consideration of the appended claims and drawings.

1. A gimbaled mount system for satellites, the system comprising:environmentally exposed components, which are made of heavy gauge marinegrade stainless steel; and four legs with screw adjustable feet.
 2. Thesystem according to claim 1, wherein: the heavy gauge stainless steel isat least 0.025 inches thick.
 3. The system according to claim 1, furthercomprising: a system of non-motorized wind damping.
 4. The systemaccording to claim 1, further comprising: a system of motorized winddamping.
 5. The system according to claim 4, further comprising: anelectric stepper motor, mounted on a slide on sleeve and a bracketassembly on one of four legs, wherein the stepper motor is connected bya common control cable assembly that is shared by an aerometer unit andis routed back to a controller, wherein the aerometer unit iselectrically connected by a common control cable along with the steppermotor assembly back to the controller, and together the stepper motorand aerometer provide an electric automatic wind dampening system. 6.The system according to claim 5, further comprising: aerometer cups,wherein an action of wind turning the aerometer cups causes a signalvoltage relative to current wind speed to be fed back to the controllerfor controlling the stepper motor.
 7. The system according to claim 1,further comprising: a system of non-motorized wind damping; and a systemof motorized wind damping.
 8. A method of non-motorized wind damping ona gimbaled mount system for satellites, the method comprising: rotatingof a dampening spool to cause all tension springs to be equally tensionloaded.
 9. A gimbaled mounting system for satellites, the systemcomprising: a satellite dish; a low noise amplifier module; pivotpoints; a thermal heating cord along the backside of the satellite dish,along an underside of the low noise amplifier module, and along crucialpivot points of the gimbaled mounting system; and a thermostat set whichregulates the thermal heating cord.